网络化DNC系统的嵌入式解决方法

叙述了在网络化DNC系统中引入嵌入式系统方案的必要性;在试验验证的基础上,提出了一套基于嵌入式系统的设计方法,以解决在网络化DNC系统构建过程中存在的现场数控设备多样性信息化特征之间互不兼容的问题。     

面向动态联盟环境的网络化工艺分工路线设计系统

分析了网络化工艺分工路线设计系统的 特点;介绍了系统的功能;阐述了该系统与其他系统的 信息集成并简述了系统功能的实现方法。     

风扇/压气机气动设计系统建设初探

简述了中国一航沈阳发动机设计研究所风扇/压气机气动设计系统建设的基本思路.为了积累设计经验、规范设计方法、减轻设计人员劳动强度、提高设计效率和可靠性, 在多年风扇/压气机设计及型号研制的基础上, 初步完成了可视化、网络化的风扇/压气机现代气动设计系统的建设.该系统已经过初步测试, 现已应用于工程设计中.      

基于OPC技术的气体加温压力FCS系统

介绍了基于OPC技术的气体加温压力FCS系统的设计思想、结构和特点,以及控制原理。该系统应用于航空发动机空气涡轮起动机的起动控制,形成了一体化、网络化和信息化的新型航空发动机整机试车测控系统。     

无人机地面站图像压缩传输系统设计与应用

针对无人机地面指挥控制系统要实现互连、互通、互操作的网络化要求,设计了视频信号实时网络传输和显示系统。系统由基于DSP的服务器端和通用客户端播放器组成,服务器端通过设置并行任务完成视频信号的实时采集、编码和发送,客户端完成视频信号的实时接收、解码和播放,从而使系统实现了图像信息在地面站所有显示终端上的实时显示。实验结果表明,系统完全满足无人机地面站系统功能及指标要求,并且通过网络化技术节省了地面站宝贵空间资源,系统设计方法对同类型系统具有一定借鉴意义。     

基于虚拟仪器技术的网络化惯性器件测试系统的实现

从软硬件方面介绍了一种基于虚拟仪器技术的网络化惯性器件测试系统的设计思路;由于通用性强和使用灵活,本测试系统能够推广应用到其它单机或设备的测试过程中去.     

分布式飞行器快速设计平台

该文分析研究了在网络环境下的分布式飞行器快速设计的问题。采用中间件技术构建分布式设计系统,采用CORBA技术构建了飞机快速设计的网络化设计数据库系统模型。系统中的设计模块可以彼此进行信息交流,协调设计参数,共享数据。并以简单实例说明此框架具有使用互操作技术完成不同学科、不同领域的信息交流和协同设计的特点。     

大规模定制的图形自动生成技术

介绍了定制流程的制定原则,给出了定制系统的框架模型,阐述了网络化定制系统的方法,设计了图形自动生成系统的结构,并介绍了各组成部分的内容、功能以及各部分之间的关系。最后,文章展示了图形自动生成技术的实际应用效果。     

基于数据库的新型航空发动机试验测控系统

简述了基于数据库的新型航空发动机试验测控系统的特点,介绍了一体化、信息化、网络化、智能化、标准化的航空发动机整机试验测控系统的设计思想、组成、结构和功能,为先进的新型航空发动机测控系统的应用进行了有意义地探索。     

某型机载雷达综合测试系统硬件设计

针对某系列机载雷达系统地面试验的需要,组建了一套雷达综合测试系统。该系统基于GPIB总线、VXI总线和网络化结构,采用软硬件结合的模块化设计,可进行三种型号的机载雷达的自动测试和故障诊断。雷达测试系统联试实验验证了该系统的有效性和工程实用性。     

有翼高超声速再入飞行器气动设计难点问题

有翼高超声速再入飞行器是近年来的研究热点,气动设计是飞行器设计的关键。为了更清楚地认识有翼高超声速再入飞行器气动设计的难点问题,对有翼高超声速再入飞行器的发展、优势及总体任务剖面进行了介绍,从5个方面详细介绍了该类飞行器气动设计的难点问题,包括多约束复杂面对称气动布局设计、高温真实气体效应对气动特性影响、天地差异与天地换算方法、反作用控制系统(RCS)喷流干扰对气动特性的影响以及气动数据不确定度等,简要阐明了这些难点问题对总体设计的重要性以及初步的解决思路,为有翼高超声速再入飞行器气动设计提供了一些参考。     

Simulation and Analysis of Crashworthiness of Fuel Tank for Helicopters

Crashworthiness requirement of fuel tanks is one of the important requirements in helicopter designs. The relations among the protection frame, textile layer and rubber layer of the fuel tank are introduced. Two appropriate FE models are established, one is for an uncovered helicopter fuel tank without protection frame, and the other is for fuel tank with protection frame. The dynamic responses of the two types of fuel tanks impinging on the ground with velocities of 17.3 m/s are numerically simulated for the purpose of analyzing energy-absorbing capabilities of the textile layer and protection frame. The feasibility of the current crashworthiness design of the fuel tank is examined though comparing the dynamic response behaviors of the two fuel tanks.     

The effect of inlet conditions on the flow and heat transfer in multiple rotating cavity with axial throughflow

This paper discusses experimental results from two different build configurations of a heated multiple rotating cavity test rig.Measurements of heat transfer from the discs and tangential velocities are presented.The test rig is a 70% full scale version of a high pressure compressor stack of an axial gas turbine engine.Of particular interest are the internal cylindrical cavities formed by adjacent discs and the interaction of these with a central axial throughflow of cooling air.Tests were carried out for a range of non-dimensional parameters representative of high pressure compressor internal air system flows(Re up to 5×106 and Rez up to 2×105).Two different builds have been tested.The most significant difference between these two build configurations is the size of the annular gap between the(non-rotating) drive shaft and the bores of the discs.The heat transfer data were obtained from thermocouple measurements of surface temperature and a conduction solution method.The velocity measurements were made using a two component,LDA system.The heat transfer results from the discs show differences between the two builds.This is attributed to the wider annular gap allowing more of the throughflow to penetrate into the cavity.There are also significant differences between the radial distributions of tangential velocity in the two builds of the test rig.For the narrow annular gap,there is an increase of non-dimensional tangential velocity V/Ωr with radial location to solid body rotation V/Ωr=1.For the wider annular gap,the non-dimensional velocities show a decrease with radial location to solid body rotation.      

突破技术趋同，波音再现竞争优势

 波音公司面临着来自空客公司的巨大挑战,企业战略性创新才是公司成功的关键。为此波音公司的全部战略性研究集中在扩大产品的差异性上,体现在3个方面：电子化（e-Enabled）运营环境、整体复合材料机身部件的制造技术和支持波音787客机的全球协同环境（GCE）。     

临近空间飞行器测控与信息传输系统频段选择

 临近空间飞行器是高性能信息化武器平台,测控（TT&;C）与信息传输系统是其信息保障的核心,而选择合理、可行的频段是展开系统设计的前提和基础。频段选择影响到整个技术方案的制定,是一个需综合考虑、影响深远并具有战略意义的关键问题,从国际电联（ITU）国际标准、高速数传、接收信噪比（SNR）、“三抗”、超视距中继、黑障、雨衰以及设备研制成熟度8个方面全面、细致论证了近空间平台测控系统的频段选择问题,最终得出在视距链路中以Ka频段为宜,在超视距链路中以Ku/Ka双频段为宜的结论。     

基于弯曲激波压缩系统的高超声速进气道反设计研究进展

总结了近十年来弯曲激波压缩研究的主要成果。提出了弯曲激波压缩系统的新概念,即利用特殊设计的楔形弯曲压缩面或空间弯曲压缩面,产生一系列与前缘弱激波相互交汇或叠加的压缩波系,从而使前缘激波弯曲,形成特殊的弯曲激波,它与波后的等熵压缩波来共同完成对气流的压缩。在此基础上,实现了由给定出口气动参数的超声速内流道反设计,实现了由给定压缩面压力分布和给定压缩面马赫数分布要求的型面反设计,实现了由给定激波波面的压缩型面反设计。研究证明,弯曲压缩面-弯曲激波压缩系统具有良好的综合气动性能,为高性能高超声速进气系统的气动设计提供了一种全新的设计方法。     

Experimental Study on Effects of Fuel Injection on Scramjet Combustor Performance

In order to investigate the effects of fuel injection distribution on the scramjet combustor performance, there are conducted three sets of test on a hydrocarbon fueled direct-connect scramjet test facility. The results of Test A, whose fuel injection is carried out with injectors located on the top-wall and the bottom-wall, show that the fuel injection with an appropriate close-front and centralized distribution would be of much help to optimize combustor performances. The results of Test B, whose fuel injection is performed at the optimal injection locations found in Test A, with a given equivalence ratio and different injection proportions for each injector, show that this injection mode is of little benefit to improve combustor performances. The results of Test C with a circumferential fuel injection distribution displaies the possibility of ameliorating combustor performance. By analyzing the effects of injection location parameters on combustor performances on the base of the data of Test C, it is clear that the injector location has strong coupled influences on combus- tor performances. In addition, an inner-force synthesis specific impulse is used to reduce the errors caused by the disturbance of fuel supply and working state of air heater while assessing combustor performances.     

(高)超声速流动试验技术及研究进展

近年来,与高速飞行器相关的(高)超声速流动受到了极大的关注。这类流动所具有的非定常性、强梯度和可压缩性对试验方法和风洞设计技术提出了挑战。超声速纳米示踪平面激光散射(NPLS)技术是由作者所在团队研发的非接触光学测试技术。它能够以较高的空间分辨率来揭示超声速三维流场的一个瞬态剖面的时间解析的流动结构。介绍了NPLS技术以及基于NPLS开发的密度场测量、雷诺应力测量和气动光学波前测量等方法,并回顾了这些技术在超声速边界层、超声速混合层、超声速压缩拐角、激波/边界层相互作用和光学头罩绕流等流动中的应用,清晰地再现了边界层、混合层、激波等典型流场结构及其时空演化特性。另外,为了模拟和研究高空大气条件下边界层自然转捩和超声速混合层的转捩特性,介绍了高超声速静风洞、超-超混合层风洞的设计技术以及层流化喷管的设计方法。     

Research on Auto-detection for Remainder Particles of Aerospace Relay Based on Wavelet Analysis

Aerospace relay is one kind of electronic components which is used widely in national defense system and aerospace system. The existence of remainder particles induces the reliability declining, which has become a severe problem in the development of aerospace relay. Traditional particle impact noise detection (PIND) method for remainder detection is ineffective for small particles, due to its low precision and involvement of subjective factors. An auto-detection method for PIND output signals is proposed in this paper, which is based on direct wavelet de-noising (DWD), cross-correlation analysis (CCA) and homo-filtering (HF), the method enhances the affectiv-ity of PIND test about the small particles. In the end, some practical PIND output signals are analysed, and the validity of this new method is proved.